Airstair system with deployable upper step

ABSTRACT

Airstair systems and associated methods are disclosed. In one embodiment, the airstair comprises a deployable upper step, a primary deployment device and a secondary deployment device. The upper step is movable between a stowed configuration when a door of the aircraft is closed and a deployed configuration when the door is open. The primary deployment device resiliently biases the upper step toward the deployed configuration. The secondary deployment device is movable in coordination with a movement of the door and configured to drive the deployable upper step toward the deployed configuration during opening of the door and during a failure of the primary deployment device.

CROSS REFERENCE TO RELATED APPLICATION AND CLAIM OF PRIORITY

This application relies for priority on U.S. Provisional PatentApplication Ser. No. 62/774,183 filed on Dec. 1, 2018, the entirecontent of which is incorporated herein by reference.

TECHNICAL FIELD

The disclosure relates generally to aircraft, and more particularly toan airstair of an aircraft.

BACKGROUND

Some aircraft have a built-in set of stairs called an “airstair” thatpermits passengers to board and exit the aircraft. An airstair can bebuilt into an interior side of a clamshell-style door of the aircraft.An airstair can eliminate the need for passengers to use a mobilestairway or jet bridge to board or exit the aircraft. Some airstairs cancomprise one or more deployable steps. However, existing mechanisms fordeploying such steps can be relatively complex. Improvement isdesirable.

SUMMARY

In one aspect, the disclosure describes an airstair system for anaircraft. The system comprises:

a deployable upper step movable between a stowed configuration when adoor of the aircraft is closed and a deployed configuration when thedoor is open;

a primary deployment device resiliently biasing the deployable upperstep toward the deployed configuration; and

a secondary deployment device movable in coordination with a movement ofthe door and configured to drive the deployable upper step toward thedeployed configuration during opening of the door and during a failureof the primary deployment device.

The primary deployment device may comprise a spring.

The primary deployment device may resiliently bias the upper step towardthe deployed configuration irrespective of the movement of the door.

The deployable upper step may be pivotally coupled to a fuselage of theaircraft at a pivot location that is different from a pivot location atwhich the door is pivotally coupled to the fuselage.

The deployable upper step may be pivotable about a rotation axis. Theprimary deployment device may comprise a coil spring disposed coaxiallywith the rotation axis.

The system may comprise a hinge pivotally coupling the door to thefuselage of the aircraft. The deployable upper step may interface withthe hinge when the deployable upper step is in the deployedconfiguration.

The hinge may define an upper stepping surface. The deployable upperstep may extend the upper stepping surface defined by the hinge when thedeployable upper step is in the deployed configuration.

The secondary deployment device may comprise a command lever pivotallycoupled to the fuselage of the aircraft and drivingly coupled forcoordinated movement with the movement of the door.

The secondary deployment device may comprise a first engaging member.The deployable upper step may comprise a second engaging member forengaging with the first engaging member.

The second engaging member may be movable relative to the deployableupper step between a ceding position allowing the first engaging memberto move past the second engaging member, and a interfering positioninterfering with movement of the first engaging member. The secondengaging member may be resiliently biased toward the interferingposition.

The first engaging member may move the second engaging member toward theceding position during a closing movement of the door. The firstengaging member may drivingly engage the deployable upper step via thesecond engaging member during an opening movement of the door.

The second engaging member may be pivotally coupled to the deployableupper step and may be resiliently biased against a hard stop definingthe interfering position of the second engaging member.

The system may comprise a hinge pivotally coupling the door to thefuselage of the aircraft. The secondary deployment device may comprise:

a command lever pivotally coupled to the fuselage; and

a link having a first end pivotally coupled to the command lever and anopposite second end pivotally coupled to the hinge.

The command lever of the secondary deployment device may comprise afirst engaging member. The deployable upper step may comprise a secondengaging member for engaging with the first engaging member.

The secondary deployment device may drive the deployable upper steptoward the stowed configuration during closing of the door.

The deployable upper step may be pivotally coupled to the fuselage ofthe aircraft.

The secondary deployment device may be configured to pull the deployableupper step toward the deployed configuration.

Embodiments can include combinations of the above features.

In another aspect, the disclosure describes a method for actuating adeployable upper step of an airstair of an aircraft. The methodcomprises:

using a primary deployment device, resiliently biasing the deployableupper step toward a deployed configuration during opening of a door ofthe aircraft; and

using a secondary deployment device movable in coordination with amovement of the door, driving the deployable upper step toward thedeployed configuration during opening of the door and during a failureof the primary deployment device.

The method may comprise resiliently biasing the upper step toward thedeployed configuration irrespective of the movement of the door.

The deployable upper step may be pivotable about a rotation axisdifferent from a rotation axis of the door.

The method may comprise using the secondary deployment device to drivethe deployable upper step toward the stowed configuration during closingof the door.

The deployable upper step may be pivotally coupled to the fuselage ofthe aircraft.

The method may comprise using the secondary deployment device to pullthe deployable upper step toward the deployed configuration.

Embodiments can include combinations of the above features.

In another aspect, the disclosure describes an airstair system for anaircraft. The system comprises:

a deployable upper step movable between a stowed configuration and adeployed configuration, the deployable upper step being pivotallycoupled to a fuselage of the aircraft at a first pivot location; and

a door pivotally coupled to the fuselage at a second pivot locationdifferent from the first pivot location, the door having an interiorside facing an interior of the aircraft when the door is closed anddefining one or more other steps cooperating with the deployable upperstep to define an airstair.

The system may comprise a hinge pivotally coupling the door to thefuselage. The deployable upper step interfaces with the hinge when thedeployable upper step is in the deployed configuration.

The hinge may define an upper stepping surface. The deployable upperstep may extend the upper stepping surface defined by the hinge when thedeployable upper step is in the deployed configuration.

The upper step is resiliently biased toward the deployed configurationirrespective of a position of the door.

The system may comprise a device movable in coordination with a movementof the door and configured to drive the deployable upper step toward thestowed configuration during closing of the door.

Embodiments can include combinations of the above features.

In another aspect, the disclosure describes a method for actuating adeployable upper step of an airstair of an aircraft. The methodcomprises:

deploying the deployable upper step of the airstair toward a deployedconfiguration by pivoting the deployable upper step about a first pivotlocation, the deployable upper step being pivotally coupled to afuselage of the aircraft at the first pivot location; and

opening a door pivotally coupled to the fuselage at a second pivotlocation different from the first pivot location, the door having aninterior side facing an interior of the aircraft when the door is closedand defining one or more other steps cooperating with the deployableupper step to define an airstair.

The door may be pivotally coupled to the fuselage via a hinge. Themethod may comprise causing the deployable upper step to interface withthe hinge when the deployable upper step is in the deployedconfiguration.

The hinge may define an upper stepping surface. The method may comprisesusing the deployable upper step to extend the upper stepping surfacedefined by the hinge when the deployable upper step is in the deployedconfiguration.

The method may comprise resiliently biasing the upper step toward thedeployed configuration irrespective of a position of the door.

The method may comprise driving the deployable upper step toward thestowed configuration during closing of the door.

Embodiments can include combinations of the above features.

In a further aspect, the disclosure describes an aircraft comprising theairstair system as described herein.

Further details of these and other aspects of the subject matter of thisapplication will be apparent from the detailed description includedbelow and the drawings.

DESCRIPTION OF THE DRAWINGS

Reference is now made to the accompanying drawings, in which:

FIG. 1 is a top plan view of an exemplary aircraft comprising anairstair system as described herein;

FIG. 2 is a perspective view of a portion of a fuselage of the aircraftof FIG. 1 with an exemplary airstair system;

FIG. 3 is a perspective view of an upper portion of the airstair of FIG.2 showing an exemplary deployable upper step;

FIG. 4 is a perspective view of a spring resiliently biasing thedeployable upper step of FIG. 3 toward a deployed configuration;

FIG. 5 is a side view of the upper portion of the airstair showing thedeployable upper step in the stowed configuration;

FIG. 6 is a side view of the upper portion of the airstair showing thedeployable upper step in a stage where a door of the aircraft is betweenopen and closed positions;

FIG. 7 is a side view of the upper portion of the airstair showing thedeployable upper step in another stage where a door of the aircraft isbetween open and closed positions;

FIG. 8 is a side view of the upper portion of the airstair showing thedeployable upper step in the deployed configuration;

FIG. 9 is a perspective view of an engaging member of the deployableupper step;

FIG. 10 is a side view showing engagement of a secondary deploymentdevice with the upper step;

FIGS. 11A-11D are side views showing sequential steps to establishengagement of the secondary deployment device with the upper step;

FIG. 12 is a flowchart of a method for actuating a deployable upper stepof an airstair; and

FIG. 13 is a flowchart of another method for actuating a deployableupper step of an airstair.

DETAILED DESCRIPTION

In various embodiments, the airstair systems and associated methodsdescribed herein can facilitate the deployment and stowing of one ormore deployable upper steps of an airstair of an aircraft. The systemsdisclosed herein can permit a deployment and stowing of the upper stepthat is coordinated (e.g., synchronized) with the opening and closing ofthe door. In some embodiments, the systems disclosed herein can have arelatively simple construction compared to other existing systems andcan also facilitate maintenance of the airstair by permitting manuallifting of the upper step to provide access under the upper step withoutrequiring (e.g., significant or any) disassembly of the upper step orother part(s) of the airstair. The deployable upper step disclosedherein can provide a relatively stable and large stepping surface forpassengers and can have an aesthetically pleasing and clean appearance.

In various embodiments, the airstair system described herein comprises aprimary deployment device (e.g., spring(s)) that resiliently biases thedeployable upper step toward the deployed configuration. The airstaircan also comprise a secondary deployment device movable in coordinationwith a movement of the door of the aircraft and that is configured todrive (e.g., pull) the deployable upper step toward the deployedconfiguration during opening of the door in the event of a failure ofthe primary deployment device. Aspects of various embodiments aredescribed through reference to the drawings.

FIG. 1 is a top plan view of an exemplary aircraft 10 which can comprisedoor 12 and airstair system 14 as described herein. Aircraft 10 can be afixed-wing aircraft comprising one or more engines 15. Aircraft 10 cancomprise wings 16, fuselage 18 and empennage 20. Aircraft 10 can be anytype of aircraft such as corporate, private, commercial and passengeraircraft suitable for civil aviation. For example, aircraft 10 can be a(e.g., ultra-long range) business jet, a twin-engine turboprop airlineror a regional jet airliner.

FIG. 2 is a perspective view of a portion of fuselage 18 with door 12 ofaircraft 10 shown in an open position. Door 12 can be a clamshell-styledoor. Airstair system 14 can be integrated with door 12. Door 12 can bepivotally coupled to fuselage 18 of aircraft 10 via hinge 22 disposed ata lower portion of opening 24 formed into fuselage 18. Door 12 can havean interior side facing an interior (e.g., passenger cabin) of aircraft10 when door 12 is closed and an exterior side (e.g., outer skin) facingan exterior of aircraft 10 when door 12 is closed. The interior side ofdoor 12 can define an airstair that is part of airstair system 14 andpermit passengers to board and exit aircraft 10 when door 12 is open.Airstair system 14 can comprise deployable upper step 26 movable betweena stowed configuration when door 12 is closed and a deployedconfiguration when door 12 is open. Airstair system 14 can comprise oneor more fixed (i.e., non-deployable) steps 28 that are disposed belowdeployable upper step 26 on airstair system 14 when door 12 is open.Airstair system 14 can also include deployable handrail 30. Handrail 30can be movable between a stowed configuration when door 12 is closed toa deployed configuration when door 12 is open.

FIG. 3 is a perspective view of an upper portion of airstair system 14showing an exemplary deployable upper step 26. Upper step 26 cancomprise a single panel that is pivotally coupled to part of fuselage 18(i.e., main body) of aircraft 10. Upper step 26 can be pivotally coupledto fuselage 18 at a pivot location that is different from a pivotlocation at which door 12 is pivotally coupled to fuselage 18 via hinge22. Accordingly, upper step 26 can be rotatable about rotation axis A1that is different from rotation axis A2 of door 12. Rotation axis A1 ofupper step 26 can be parallel but spaced apart from rotation axis A2 ofdoor 12.

Deployable upper step 26 can be movable between a stowed configurationas shown in FIG. 3 when door 12 is closed and a deployed configuration(see FIG. 8) when door 12 is open. Airstair system 14 can compriseprimary deployment device 32 (shown in FIG. 4) resiliently biasing upperstep 26 toward the deployed configuration. Airstair system 14 can alsocomprise mechanism 34 shown in FIGS. 6-8 and movable in coordinationwith a movement of door 12. Mechanism 34 can serve as a secondarydeployment device for driving upper step 26 toward the deployedconfiguration during opening of door 12 in the event of a failure ofprimary deployment device 32. Mechanism 34 can also be configured todrive upper step 26 toward the stowed configuration during closing ofdoor 12.

Mechanism 34 can comprise command lever 36 having a first end 36A thatis pivotally coupled to fuselage 18. Mechanism 34 can also comprise link38 having first end 38A pivotally coupled to command lever 36 and anopposite second end 38B pivotally coupled to hinge 22. Command lever 36of mechanism 34 can comprises first engaging member 40. First engagingmember 40 can be a boss or a roller protruding from a side of commandlever 36. Upper step 26 can comprise second engaging member 42 forengagement with first engaging member 40. As explained further below,the engagement of first engaging member 40 with second engaging member42 can permit mechanism 34 to pull upper step 26 toward the deployedconfiguration.

FIG. 4 is a perspective view of primary deployment device 32 resilientlybiasing deployable upper step 26 toward the deployed configuration. Insome embodiments, primary deployment device 32 can comprise one or moresprings 44. In some embodiments, such springs 44 can be torsion (e.g.,coil) springs that are disposed coaxially with rotation axis A1 of upperstep 26. Spring(s) 44 can be disposed at a hinge/pivot location betweenupper step 26 and fuselage 18. Spring(s) 44 can be disposed at acoupling location of upper step 26 and fuselage 18.

Spring(s) 44 can be configured to apply a torque between upper step 26and fuselage 18 in order to resiliently bias upper step 26 toward thedeployed configuration. In some embodiments, spring(s) 44 can beconfigured to resiliently bias upper step 26 toward the deployedconfiguration irrespectively of the movement or position of door 12. Forexample, spring(s) 44 can be configured to resiliently bias upper step26 toward the deployed configuration when door 12 is closed, when door12 is open, when door 12 is undergoing a closing movement and/or whendoor 12 is undergoing an opening movement. Airstair system 14 cancomprise one primary deployment device 32 or a plurality of primarydeployment devices 32 disposed at different locations along rotationaxis A1 for example. Other types (e.g., linear) springs could be used toresiliently bias upper step 26 toward the deployed configuration.

FIG. 5 is a side view of the upper portion of the airstair showing upperstep 26 in the stowed configuration when door 12 is closed. Secondengaging member 42 has been omitted from FIG. 5 to show the location ofprimary deployment device 32. In this configuration, upper step 26 canbe in a generally upright position and held in such position by one offixed steps 28 making contact with an underside of upper step 26. Fixedstep 28 can hold upper step 26 in the stowed configuration by pushingagainst upper step 26 to counteract and overcome the opposite biasingtorque that can be applied by primary deployment device 32.

In some embodiments, door 12 can be configured so that the opening andclosing of door 12 can be initiated manually either by the flight crewfrom the interior of aircraft 10 or by the ground crew from the exteriorof aircraft 10. In some embodiments door 12 can be coupled to an assistmechanism configured to reduce an amount of force required to manuallymove door 12 between its open and closed positions. In some embodiments,door 12 can be operatively coupled to one or more electric motors 46that can facilitate the opening and/or closing of door 12 for example.Motor 46 can be mounted to fuselage 18 and drivingly coupled to door 12via cable(s) 48 (shown in FIG. 2) and pulley(s). Door 12 can compriseother (e.g., latching, locking) mechanisms and components that have beenomitted from the figures for clarity.

FIG. 6 is a side view of the upper portion of the airstair showing upperstep 26 in a stage where door 12 is between the open and closedpositions. The deployment and stowing of upper step 26, illustrated byrotation R26 of upper step 26 about rotation axis A1, can be coordinatedwith the opening and closing movement of door 12, illustrated byrotation R22 of hinge 22 about rotation axis A2. Command lever 36 ofsecondary deployment device 32 can comprise guide 50 disposed at secondend 36B of command lever 36 opposite first end 36A of command lever 36.Guide 50 can comprise a roller or other member(s) configured forcontacting an underside of upper step 26. During deployment of upperstep 26, guide 50 can make contact with upper step 26 in order to opposethe deployment torque applied by primary deployment device 32 andcontrol the deployment movement of upper step 26 based on the openingmovement of door 12 transferred to guide 50 via command lever 36, link38 and hinge 22. During stowing of upper step 26, guide 50 can makecontact with upper step 26 in order to oppose the deployment torqueapplied by primary deployment device 32 and controllably drive (e.g.,urge) upper step 26 toward its stowed configuration based on the closingmovement of door 12 transferred to guide 50 via command lever 36, link38 and hinge 22.

FIG. 7 is a side view of the upper portion of the airstair showing upperstep 26 in another stage where door 12 is between the open and closedpositions. FIG. 7 also shows an enlarged region where upper step 26 caninterface with hinge 22 when upper step 26 is in the deployedconfiguration. Upper step 26 can comprise shoulder surface 52 and hinge22 can comprise shoulder surface 54. Shoulder surfaces 52, 54 can becomein contact with each other when upper step 26 is deployed so that hinge22 can provide support and stability for upper step 26. For example, theinterfacing of shoulder surfaces 52, 54 can cause load from passengersstepping on upper step 26 to be transferred into fuselage 18 via hinge22 instead of via mechanism 34 including command lever 36 and link 38.

FIG. 8 is a side view of the upper portion of the airstair showing upperstep 26 in the deployed configuration. FIG. 8 includes an enlargedregion showing gap G between guide 50 and upper step 26 when upper step26 is in the deployed configuration. As explained in relation to FIG. 7above, the interfacing of shoulder surfaces 52, 54 can provide adequatesupport for upper step 26 during use so that mechanism 34 includingcommand lever 36 and link 38 does not have to provide the requiredsupport for upper step 26. Accordingly, mechanism 34 including commandlever 36 and link 38 does not need to be designed to have a stiffnesstailored to accommodate the load of passenger(s) stepping or standing onupper step 26. The presence of gap G can prevent or reduce the amount ofpassenger load that gets transferred into command lever 36 and link 38.In some embodiments, airstair system 14 can comprise a plurality ofmechanisms 34 disposed along the width of upper step 26 and the presenceof gap G can prevent force fight between different mechanisms 34.

In some embodiments, hinge 22 can comprise fixed step 28 that definesupper stepping surface 28A and upper step 26 can extend upper steppingsurface 28A defined by hinge 22 when upper step 26 is in the deployedconfiguration as shown in FIG. 8. The size (area) of the upper steppingsurface cooperatively defined by fixed step 28 and upper step 26 can berelatively large and can, in some embodiments, be substantially the sameas an area of footwell 56 disposed at the top of airstair system 14 andbelow cabin floor 58.

In some embodiments, one or more side tabs 60 can be fixed to upper step26. For example, one side tab 60 can be disposed on each lateral side ofupper step 26 in order to be disposed to each lateral sides of fixedstep 28 defined by hinge 22 when upper step 26 is deployed. Side tabs 60can occlude gaps on each side of fixed step 28 in order to prevent smallobjects that can be dropped by passengers from being lost insideairstair system 14 via such gaps.

When upper step 26 is deployed as shown in FIG. 8, upper step 26 can bemanually lifted by maintenance personnel for example to access theregion of airstair system 14 that is disposed under upper step 26 forinspection, repair or service. The torque or other force provided byprimary deployment device 32 (shown in FIG. 4) can be selected to behigh enough to cause deployment of upper step 26 while being low enoughto permit manual lifting by maintenance personnel. Manual lifting ofupper step 26 can cause rotation of upper step 26 about rotation axis A1while opposing and overcoming the torque provided by primary deploymentdevice 32. During such manual lifting, command lever 36 and link 38would remain in their respective positions shown in FIG. 8 in order topermit second engaging member 42 to move without engaging with firstengaging member 40 of command lever 36. In some embodiments, tab 60 canserve as a handle to facilitate the manual lifting of upper step 26 bymaintenance personnel.

FIG. 9 is a perspective view of second engaging member 42 of upper step26. Second engaging member 42 can be secured (e.g., fastened) to theunderside of upper step 26 via support 62. Second engaging member 42 cancomprise a paddle pivotally coupled to support 62 and be rotatable aboutrotation axis A3. Second engaging member 62 can be movable (e.g.,rotatable) between a ceding position (shown in FIG. 110) allowing firstengaging member 40 to move past second engaging member 42, and aninterfering position (shown in FIGS. 9 and 10) interfering with movementof first engaging member 40. Second engaging member 42 can beresiliently biased toward the interfering position via spring 64. Spring64 can be a torsion (e.g., coil) spring that is disposed coaxially withrotation axis A3 and that is configured to apply a torque on secondengaging member 42. Second engaging member 42 can be resiliently biasedagainst hard stop 66 which defines the interfering position of secondengaging member 42.

FIG. 10 is a side view showing engagement between first engaging member40 of command lever 36 and second engaging member 42 of upper step 26.Even though primary deployment device 32 may be adequate for causingdeployment of upper step 26 during opening movement of door 12, someregulations may mandate the presence of a backup (i.e., failsafe)mechanism/device that can cause the deployment of upper step 26 in theevent of a failure of primary deployment device 32 especially where door12 is also intended to be used as an emergency exit. Such failure can beany situation (e.g., spring failure/break, sticking of upper step 26 orother issue) where primary deployment device 32 would not be able tocause deployment of upper step 26 during opening of door 12.Accordingly, mechanism 34 can be configured to cause deployment of upperstep 26 by pulling upper step 26 toward its deployed configuration. Thepulling of upper step 26 can be coordinated with the opening movement ofdoor 12 through the use of link 38 and command lever 36.

During normal deployment and stowing of upper step 26 when primarydeployment device 32 is in proper operating order, first engaging member40 may not become engaged with second engaging member 42 as shown in thepreceding figures. However, in the event where door 12 is opening butupper step 26 does not deploy under the influence of primary deploymentdevice 32, counter-clockwise rotation R36 of command lever 36 as shownin FIG. 10 would cause first engaging member 40 to engage with secondengaging member 42 and thereby pull upper step 26 toward the deployedconfiguration from the stowed configuration. As shown in FIG. 7, thekinematics arrangement of mechanism 34 can be configured so that firstengaging member 40 does not pull upper step 26 all the way to thedeployed configuration. For example, mechanism 34 can be configured sothat first engaging member 40 pulls upper step 26 only part way to thedeployed configuration and then gravity acting on upper step 26 cancause upper step 26 to reach its fully deployed configuration.

FIGS. 11A-11D depict sequential steps for causing engagement of firstengaging member 40 and second engaging member 42 in case where door 12is open while upper step 26 is in the stowed configuration. This canrepresent a maintenance situation where upper step 26 has been liftedmanually and has been left resting on guide 50 while door 12 ispartially open or upper step 26 is otherwise caused to be in the stowedconfiguration while door 12 is not closed. In other words, in case upperstep 26 is left in the stowed configuration while door is open, the nextcycle of closing/opening of door 12 can cause re-engagement of mechanism34 with upper step 26.

FIG. 11A shows a step where command lever 36 is rotating in theclockwise direction due to the closing movement of door 12. Firstengaging member 40 is approaching second engaging member 42 which is inthe interfering position.

FIG. 11B shows a subsequent step where command lever 36 continues torotate in the clockwise direction due to the closing movement of door12. First engaging member 40 contacts and pushes second engaging member42 away from the interfering position of FIG. 11A in order to oppose andovercome the torque applied to second engaging member 42 by spring 64(shown in FIG. 9).

FIG. 11C shows a subsequent step where command lever 36 continues torotate in the clockwise direction due to the closing movement of door12. First engaging member 40 has pushed second engaging member 42 to itsceding position where first engaging member 40 is permitted to pass bysecond engaging member 42.

FIG. 11D shows a subsequent step where second engaging member 42 hasreturned to its interfering position defined by hard stop 66 (shown inFIG. 9) due to the influence of spring 64 after first engaging member 40has moved past second engaging member 42 and has released secondengaging member 42. FIG. 11D shows command lever 36 rotating in thecounter-clockwise direction prior to causing engagement of firstengaging member 40 with second engaging member 42 and returning to theconfiguration illustrated in FIG. 10.

FIG. 12 is a flowchart of a method 100 for actuating deployable upperstep 26 of an airstair. Method 100 can be conducted using airstairsystem 14 described herein. Method 100 can comprise:

using primary deployment device 32, resiliently biasing upper step 26toward the deployed configuration during opening of door 12 of aircraft10 (see block 102); and

using a secondary deployment device (e.g., mechanism 34) movable incoordination with the movement of door 12, driving upper step 26 towardthe deployed configuration during opening of door 12 and during afailure of primary deployment device 32 (see block 104).

Upper step 26 can be pivotable about rotation axis A1 different fromrotation axis A3 of door 12. Upper step 26 can be pivotally coupled tofuselage 18 of aircraft 10.

Method 100 can comprise resiliently biasing upper step 26 toward thedeployed configuration irrespective of the movement and/or position ofdoor 12.

Method 100 can comprise using secondary deployment device (e.g.,mechanism 34) to drive upper step 26 toward the stowed configurationduring closing of door 12.

Method 100 can comprise using secondary deployment device (e.g.mechanism 34) to pull upper step 26 toward the deployed configuration.

FIG. 13 is a flowchart of a method 200 for actuating deployable upperstep 26 of an airstair. Method 200 can be conducted using airstairsystem 14 described herein. Method 200 can comprise:

deploying upper step 26 of the airstair toward the deployedconfiguration by pivoting upper step 26 about a first pivot location,upper step 26 being pivotally coupled to fuselage 18 of aircraft 10 atthe first pivot location (see block 202); and

opening door 12 pivotally coupled to fuselage 12 at a second pivotlocation different from the first pivot location, door 12 having aninterior side facing an interior of aircraft 10 when door 12 is closedand defining one or more other steps 28 cooperating with upper step 26to define an airstair (see block 204).

Door can be pivotally coupled to fuselage 18 via hinge 22. Method 200can comprise causing upper step 26 to interface with hinge 22 when upperstep 26 is in the deployed configuration.

Hinge 22 can define upper stepping surface 28A. Method 200 can compriseusing upper step 26 to extend upper stepping surface 28A defined byhinge 22 when upper step 26 is in the deployed configuration.

Method 200 can comprise resiliently biasing upper step 26 toward thedeployed configuration irrespective of a position and/or movement ofdoor 12.

Method 200 can comprise driving upper step 26 toward the stowedconfiguration during closing of the door.

The above description is meant to be exemplary only, and one skilled inthe relevant arts will recognize that changes may be made to theembodiments described without departing from the scope of the inventiondisclosed. The present disclosure may be embodied in other specificforms without departing from the subject matter of the claims. Thepresent disclosure is intended to cover and embrace all suitable changesin technology. Modifications which fall within the scope of the presentinvention will be apparent to those skilled in the art, in light of areview of this disclosure, and such modifications are intended to fallwithin the appended claims. Also, the scope of the claims should not belimited by the preferred embodiments set forth in the examples, butshould be given the broadest interpretation consistent with thedescription as a whole.

1. An airstair system for an aircraft, the system comprising: adeployable upper step movable between a stowed configuration when a doorof the aircraft is closed and a deployed configuration when the door isopen; a primary deployment device resiliently biasing the deployableupper step toward the deployed configuration; and a secondary deploymentdevice movable in coordination with a movement of the door andconfigured to drive the deployable upper step toward the deployedconfiguration during opening of the door and during a failure of theprimary deployment device.
 2. The system as defined in claim 1, whereinthe primary deployment device comprises a spring.
 3. The system asdefined in claim 1, wherein the primary deployment device resilientlybiases the upper step toward the deployed configuration irrespective ofthe movement of the door.
 4. The system as defined in claim 1, whereinthe deployable upper step is pivotally coupled to a fuselage of theaircraft at a pivot location that is different from a pivot location atwhich the door is pivotally coupled to the fuselage.
 5. The system asdefined in claim 1, wherein: the deployable upper step is pivotableabout a rotation axis; and the primary deployment device comprises acoil spring disposed coaxially with the rotation axis.
 6. The system asdefined in claim 1, comprising a hinge pivotally coupling the door to aor the fuselage of the aircraft, the deployable upper step interfacingwith the hinge when the deployable upper step is in the deployedconfiguration.
 7. The system as defined in claim 6, wherein: the hingedefines an upper stepping surface; and the deployable upper step extendsthe upper stepping surface defined by the hinge when the deployableupper step is in the deployed configuration.
 8. The system as defined inclaim 1, wherein the secondary deployment device comprises a commandlever pivotally coupled to a or the fuselage of the aircraft anddrivingly coupled for coordinated movement with the movement of thedoor.
 9. The system as defined in claim 8, wherein: the secondarydeployment device comprises a first engaging member; the deployableupper step comprises a second engaging member for engaging with thefirst engaging member.
 10. The system as defined in claim 9, wherein:the second engaging member is movable relative to the deployable upperstep between a ceding position allowing the first engaging member tomove past the second engaging member, and a interfering positioninterfering with movement of the first engaging member; and the secondengaging member is resiliently biased toward the interfering position.11. The system as defined in claim 10, wherein: the first engagingmember moves the second engaging member toward the ceding positionduring a closing movement of the door; and the first engaging memberdrivingly engages the deployable upper step via the second engagingmember during an opening movement of the door.
 12. The system as definedin claim 10, wherein the second engaging member is pivotally coupled tothe deployable upper step and is resiliently biased against a hard stopdefining the interfering position of the second engaging member.
 13. Thesystem as defined in claim 1, comprising a hinge pivotally coupling thedoor to a fuselage of the aircraft, wherein the secondary deploymentdevice comprises: a command lever pivotally coupled to the fuselage; anda link having a first end pivotally coupled to the command lever and anopposite second end pivotally coupled to the hinge.
 14. The system asdefined in claim 13, wherein: the command lever of the secondarydeployment device comprises a first engaging member; and the deployableupper step comprises a second engaging member for engaging with thefirst engaging member.
 15. The system as defined in claim 1, wherein thesecondary deployment device drives the deployable upper step toward thestowed configuration during closing of the door. 16.-24. (canceled) 25.An airstair system for an aircraft, the system comprising: a deployableupper step movable between a stowed configuration and a deployedconfiguration, the deployable upper step being pivotally coupled to afuselage of the aircraft at a first pivot location; and a door pivotallycoupled to the fuselage at a second pivot location different from thefirst pivot location, the door having an interior side facing aninterior of the aircraft when the door is closed and defining one ormore other steps cooperating with the deployable upper step to define anairstair.
 26. The system as defined in claim 25, comprising a hingepivotally coupling the door to the fuselage, wherein the deployableupper step interfaces with the hinge when the deployable upper step isin the deployed configuration.
 27. The system as defined in claim 26,wherein: the hinge defines an upper stepping surface; and the deployableupper step extends the upper stepping surface defined by the hinge whenthe deployable upper step is in the deployed configuration.
 28. Thesystem as defined in claim 25, wherein the upper step is resilientlybiased toward the deployed configuration irrespective of a position ofthe door.
 29. The system as defined in claim 28, comprising a devicemovable in coordination with a movement of the door and configured todrive the deployable upper step toward the stowed configuration duringclosing of the door. 30.-35. (canceled)